US7342765B2 - Current insulation device for fuel systems - Google Patents

Current insulation device for fuel systems Download PDF

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Publication number
US7342765B2
US7342765B2 US11/359,774 US35977406A US7342765B2 US 7342765 B2 US7342765 B2 US 7342765B2 US 35977406 A US35977406 A US 35977406A US 7342765 B2 US7342765 B2 US 7342765B2
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United States
Prior art keywords
fuel system
linear component
risks
forming part
component forming
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US11/359,774
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US20070145190A1 (en
Inventor
Eduardo Orgaz Villegas
Jorge Nogal Martin
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Airbus Operations SL
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Airbus Espana SL
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Assigned to AIRBUS ESPANA, S.L. reassignment AIRBUS ESPANA, S.L. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: NOGAL MARTIN, JORGE, ORGAZ VILLEGAS, EDUARDO
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Assigned to AIRBUS OPERATIONS S.L. reassignment AIRBUS OPERATIONS S.L. CHANGE OF NAME (SEE DOCUMENT FOR DETAILS). Assignors: AIRBUS ESPANA, S.L.
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D45/00—Aircraft indicators or protectors not otherwise provided for
    • B64D45/02—Lightning protectors; Static dischargers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D37/00—Arrangements in connection with fuel supply for power plant
    • B64D37/32—Safety measures not otherwise provided for, e.g. preventing explosive conditions
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
    • F16L25/00—Constructive types of pipe joints not provided for in groups F16L13/00 - F16L23/00 ; Details of pipe joints not otherwise provided for, e.g. electrically conducting or insulating means
    • F16L25/02—Electrically insulating joints or couplings
    • F16L25/026—Electrically insulating joints or couplings for flanged joints
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S439/00—Electrical connectors
    • Y10S439/933—Special insulation
    • Y10S439/934—High voltage barrier, e.g. surface arcing or corona preventing insulator

Definitions

  • the invention relates to an insulation device inserted in a linear component forming part of a fuel system subjected to risks of possible electrical discharges and, more particularly, to a device for protecting aircraft fuel systems from electrical discharges caused by lightning strikes on fuel tanks manufactured with materials with low electrical conductivity.
  • Composites offer high electrical resistance when compared to metallic materials.
  • the latter have been traditionally used in the aeronautical field for manufacturing structures intended to fuel storage, given the mechanical features these materials have with respect to their weight.
  • the high electrical resistance inherent to composites causes a highly relevant induction effect on the internal systems of the fuel tank. Said effect induces internal electric currents that may generate failures or phenomena which are catastrophic for overall structural integrity.
  • Hot spots the high current density in certain specific locations of the structure such as joints or intersection components, can originate high temperature spots. If this temperature exceeds 200° C. (the autoignition point of fuel considered by the FAA/JAA authorities) the fuel may reach its flash point should the suitable stoichiometric concentrations be present inside the tank.
  • Electric arcs sparking: the flow of current through materials with different resistivities and in geometrically separated locations can produce voltage drops between amongst one another, releasing discharges in the form of an electric arc and causing the ignition of the fuel/inflammable liquid or vapours contained within the structure.
  • Patent application PCT/ES05/070133 by the applicant of the present invention describes a method for protecting the set of metal devices arranged inside an electrical discharge-proof fuel tank, manufactured completely or partially with composites, which considers, amongst other items, including insulating inserts in the linear metal devices such that they are subdivided into parts that are insulated from each other.
  • the present invention refers to an insert of this type that may be used in places with little space available.
  • the present invention proposes an electrical insulation device for a linear component, for example a pipe, which forms part of a fuel system subjected to risks of possible external electrical discharges that is formed by a part made of an insulating material joined to two metal flanges allowing the insertion of the device between two parts of said linear component.
  • the part made of insulating material is constituted by a cylindrical body with a castellated crown on its outer side, formed by longitudinal (in the same direction as the axis of the cylindrical body) and transverse (in a perpendicular direction to the axis of the cylindrical body) segments.
  • the flanges include transverse projections facing the transverse segments of the castellated crown to allow their attachment by suitable means.
  • the device object of the present invention may be applied to fuel and ventilation lines forming part of the fuel systems installed in aircraft, when it is necessary to stop the current or rather insulate sections of the installation in which the passage thereof is intended, and the space available is small.
  • FIG. 1 shows side elevational and front sectional views of the electrical insulation device according to the present invention.
  • FIG. 2 shows a perspective view of the electrical insulation device according to the invention.
  • device 11 is formed by a part 13 made of insulating material attached to two metal flanges 15 , 17 for facilitating insertion of the device between two parts of the linear component (for example, a pipe) to be insulated.
  • the linear component for example, a pipe
  • the insulating part 13 is formed by a cylindrical body 21 with a castellated crown 23 on its outer side, formed by longitudinal 25 and transverse 27 segments.
  • the flanges 15 , 17 have, respectively, transverse projections 31 , 33 facing the transverse segments 27 of the castellated crown 23 in order to facilitate their attachment by suitable means, such as screws 39 .
  • the insulating part 13 can be made by machining or by injection moulding an insulating material (nylon, polyamide) with the mentioned castellated shape which prevents the passage of current when it is circulating along the fuel or ventilation lines in which the device is inserted and allows providing efficient insulating devices when there are space limitations in the fuel system installation.
  • an insulating material nylon, polyamide
  • said part 13 undergoes various insulation tests during which it is subjected to a potential difference between the ends thereof at 500 VDC and at 1000 VDC, providing electrical insulation in the order of 100 Mega ohms as a minimum requirement.
  • the length of the insulating part 13 is comprised between 25-80 mm which allows complying with its electrical insulation function without becoming statically charged.
  • the device 11 according to the invention is applicable, as has been mentioned above, to fuel installations in which the current is intended to be insulated in sections or when a single bonding point philosophy is intended to be applied.
  • the device object of the present invention is also applicable to other systems other than fuel, such as for example the hydraulic or pneumatic circuit, with the only variation as regards the diameter of the pipe that must be insulated.
  • the metal flanges 15 , 17 must carry some components 35 , 37 for installing a bonding point, since these systems require a double electrical bonding.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Insulating Bodies (AREA)
  • Rigid Pipes And Flexible Pipes (AREA)
  • Testing, Inspecting, Measuring Of Stereoscopic Televisions And Televisions (AREA)
  • Silver Salt Photography Or Processing Solution Therefor (AREA)
  • Measurement And Recording Of Electrical Phenomena And Electrical Characteristics Of The Living Body (AREA)
  • Insulated Conductors (AREA)
  • Elimination Of Static Electricity (AREA)
  • Fuel-Injection Apparatus (AREA)

Abstract

An electrical insulating device for a linear component forming part of a fuel system subjected to risks of possible external electrical discharges formed by a part (13) made of insulating material attached to two metal flanges (15, 17) that allow inserting the device (11) between two parts of said linear component, said part (13) being formed by a cylindrical body (21) with a castellated crown (23) on its outer side, formed by longitudinal (25) and transverse (27) segments, and said metal flanges (15, 17) having transverse projections (31, 33) facing the transverse segments (27) of the castellated crown (23) for facilitating their attachment by suitable means (39).

Description

FIELD OF THE INVENTION
The invention relates to an insulation device inserted in a linear component forming part of a fuel system subjected to risks of possible electrical discharges and, more particularly, to a device for protecting aircraft fuel systems from electrical discharges caused by lightning strikes on fuel tanks manufactured with materials with low electrical conductivity.
BACKGROUND OF THE INVENTION
Composites offer high electrical resistance when compared to metallic materials. The latter have been traditionally used in the aeronautical field for manufacturing structures intended to fuel storage, given the mechanical features these materials have with respect to their weight.
The high electrical resistance inherent to composites causes a highly relevant induction effect on the internal systems of the fuel tank. Said effect induces internal electric currents that may generate failures or phenomena which are catastrophic for overall structural integrity.
The phenomena related with moderate or severe electrical discharges occurring in the case of lightning strikes and which must be prevented in a structure manufactured with a material with low electrical conductivity to assure its structural integrity/malfunction of any of the critical electrical equipment/electric arcs inside the tank are:
Hot spots: the high current density in certain specific locations of the structure such as joints or intersection components, can originate high temperature spots. If this temperature exceeds 200° C. (the autoignition point of fuel considered by the FAA/JAA authorities) the fuel may reach its flash point should the suitable stoichiometric concentrations be present inside the tank.
Electric arcs (sparking): the flow of current through materials with different resistivities and in geometrically separated locations can produce voltage drops between amongst one another, releasing discharges in the form of an electric arc and causing the ignition of the fuel/inflammable liquid or vapours contained within the structure.
Electrical equipment malfunction: electrical discharges caused by the lightning strike give rise to high levels of current circulating through the outer structure and may therefore introduce electric current in the internal systems either by shunting or by induction. These effects are capable of causing critical equipment malfunction, generating catastrophic failures.
Patent application PCT/ES05/070133 by the applicant of the present invention describes a method for protecting the set of metal devices arranged inside an electrical discharge-proof fuel tank, manufactured completely or partially with composites, which considers, amongst other items, including insulating inserts in the linear metal devices such that they are subdivided into parts that are insulated from each other.
The present invention refers to an insert of this type that may be used in places with little space available.
SUMMARY OF THE INVENTION
The present invention proposes an electrical insulation device for a linear component, for example a pipe, which forms part of a fuel system subjected to risks of possible external electrical discharges that is formed by a part made of an insulating material joined to two metal flanges allowing the insertion of the device between two parts of said linear component.
The part made of insulating material is constituted by a cylindrical body with a castellated crown on its outer side, formed by longitudinal (in the same direction as the axis of the cylindrical body) and transverse (in a perpendicular direction to the axis of the cylindrical body) segments.
For its part, the flanges include transverse projections facing the transverse segments of the castellated crown to allow their attachment by suitable means.
The device object of the present invention may be applied to fuel and ventilation lines forming part of the fuel systems installed in aircraft, when it is necessary to stop the current or rather insulate sections of the installation in which the passage thereof is intended, and the space available is small.
Other features and advantages of the present invention will be gathered from the following detailed description of an illustrative embodiment of its object with respect to the attached figures.
BRIEF DESCRIPTION OF THE DRAWINGS
FIG. 1 shows side elevational and front sectional views of the electrical insulation device according to the present invention.
FIG. 2 shows a perspective view of the electrical insulation device according to the invention.
 DETAILED DESCRIPTION OF THE INVENTION
Following FIGS. 1 and 2 it is observed that device 11 is formed by a part 13 made of insulating material attached to two metal flanges 15, 17 for facilitating insertion of the device between two parts of the linear component (for example, a pipe) to be insulated.
The insulating part 13 is formed by a cylindrical body 21 with a castellated crown 23 on its outer side, formed by longitudinal 25 and transverse 27 segments.
The flanges 15, 17 have, respectively, transverse projections 31, 33 facing the transverse segments 27 of the castellated crown 23 in order to facilitate their attachment by suitable means, such as screws 39.
The insulating part 13 can be made by machining or by injection moulding an insulating material (nylon, polyamide) with the mentioned castellated shape which prevents the passage of current when it is circulating along the fuel or ventilation lines in which the device is inserted and allows providing efficient insulating devices when there are space limitations in the fuel system installation.
From the technical point of view, said part 13 undergoes various insulation tests during which it is subjected to a potential difference between the ends thereof at 500 VDC and at 1000 VDC, providing electrical insulation in the order of 100 Mega ohms as a minimum requirement.
In a preferred embodiment, the length of the insulating part 13 is comprised between 25-80 mm which allows complying with its electrical insulation function without becoming statically charged.
The device 11 according to the invention is applicable, as has been mentioned above, to fuel installations in which the current is intended to be insulated in sections or when a single bonding point philosophy is intended to be applied.
As long as the requirements of the material to be used (nylon, polyamide), the minimum resistance of 100 Mega ohms and the reduced dimensions due to the reasons set forth are compulsorily complied with, the device object of the present invention is also applicable to other systems other than fuel, such as for example the hydraulic or pneumatic circuit, with the only variation as regards the diameter of the pipe that must be insulated.
It is important to consider that since there is less amount of insulating material than in tubular-shaped insulating devices, the material must comply with the minimum resistance required, thus increasing the thickness of the part in comparison with other configurations.
In the case of fuel systems, the metal flanges 15, 17 must carry some components 35, 37 for installing a bonding point, since these systems require a double electrical bonding.
The preferred embodiment just described may incorporate those modifications comprised within the scope defined by the following claims.

Claims (8)

1. An electrical insulation device (11) for a linear component forming part of a fuel system subjected to risks of possible external electrical discharges, characterised in that it is formed by a part (13) made of insulating material attached to two metal flanges (15, 17) that allow inserting the device (11) between two parts of said linear component, said part (13) being formed by a cylindrical body (21) with a castellated crown (23) on its outer side, formed by longitudinal (25) and transverse (27) segments, and said metal flanges (15, 17) having transverse projections (31, 33) facing the transverse segments (27) of the castellated crown (23) for facilitating their attachment by suitable means (39).
2. An electrical insulating device (11) for a linear component forming part of a fuel system subjected to risks of possible external electrical discharges according to claim 1, characterised in that said flanges (15, 17) also include a component (35, 37) for installing a bonding point.
3. An electrical insulating device (11) for a linear component forming part of a fuel system subjected to risks of possible external electrical discharges according to claim 1, characterised in that the length of the insulating part (13) is comprised between 25 and 80 mm.
4. An electrical insulating device (11) for a linear component forming part of a fuel system subjected to risks of possible external electrical discharges according to claim 1, characterised in that the fuel system belongs to an aircraft.
5. An electrical insulating device (11) for a linear component forming part of a fuel system subjected to risks of possible external electrical discharges according to claim 2, characterised in that the length of the insulating part (13) is comprised between 25 and 80 mm.
6. An electrical insulating device (11) for a linear component forming part of a fuel system subjected to risks of possible external electrical discharges according to claim 2, characterised in that the fuel system belongs to an aircraft.
7. An electrical insulating device (11) for a linear component forming part of a fuel system subjected to risks of possible external electrical discharges according to claim 3, characterised in that the fuel system belongs to an aircraft.
8. An electrical insulating device (11) for a linear component forming part of a fuel system subjected to risks of possible external electrical discharges according to claim 5, characterised in that the fuel system belongs to an aircraft.
US11/359,774 2005-12-23 2006-02-22 Current insulation device for fuel systems Active 2026-10-28 US7342765B2 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
ESPCT/ES05/70182 2005-12-23
PCT/ES2005/070182 WO2007074177A1 (en) 2005-12-23 2005-12-23 Electric insulation device for use in fuel lines

Publications (2)

Publication Number Publication Date
US20070145190A1 US20070145190A1 (en) 2007-06-28
US7342765B2 true US7342765B2 (en) 2008-03-11

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US11/359,774 Active 2026-10-28 US7342765B2 (en) 2005-12-23 2006-02-22 Current insulation device for fuel systems

Country Status (7)

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US (1) US7342765B2 (en)
EP (1) EP1964777B1 (en)
CN (1) CN101346281B (en)
BR (1) BRPI0520793A2 (en)
CA (1) CA2634222C (en)
ES (1) ES2650553T3 (en)
WO (1) WO2007074177A1 (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20100003840A1 (en) * 2008-07-02 2010-01-07 Eaton Corporation Dielectric Isolators
US20100003438A1 (en) * 2008-07-02 2010-01-07 Miller Waste Mills d/b/a RTP Company Injection moldable, thermoplastic composite materials
US9618148B2 (en) 2008-07-02 2017-04-11 Eaton Corporation Dielectric isolators
US10040568B2 (en) 2013-01-30 2018-08-07 Short Brothers Plc Electrical protector

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2948254B1 (en) 2009-07-16 2011-12-30 Airbus Operations Sas DEVICE FOR PROTECTING PIPES AGAINST LIGHTNING
WO2011144440A1 (en) 2010-05-17 2011-11-24 Parker Hannifin Gmbh Dielectric fitting assembly
US9162774B2 (en) * 2012-06-08 2015-10-20 The Boeing Company Fluid transport system for preventing electrical discharge
US9309994B2 (en) * 2012-11-26 2016-04-12 Parker-Hannifin Corporation Dielectric fitting mounting device
US10030798B2 (en) * 2013-02-18 2018-07-24 The Boeing Company Bulkhead fitting
CA2960633A1 (en) * 2016-07-08 2018-01-08 Cci Thermal Technologies Inc. Electrically isolating block and flange for rail-heating duct
GB2572553A (en) 2018-03-29 2019-10-09 Airbus Operations Ltd Aircraft fuel tank isolator

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2393003A (en) * 1944-05-03 1946-01-15 Smith Minton Larkin Kidney catheter
US4008937A (en) * 1974-09-20 1977-02-22 Stanley Aviation Corporation Coupling assembly
US4346428A (en) * 1980-06-05 1982-08-24 Stanley Aviation Corp. Coupling assembly with bonding jumper
US4891732A (en) * 1986-11-28 1990-01-02 British Aerospace Plc Anti-lightning strike fasteners for composite material aircraft structures
US5034157A (en) * 1990-03-16 1991-07-23 Itt Corporation Injection moldable composite
US5959828A (en) * 1996-07-16 1999-09-28 Hydraflow Coupling with insulated flanges
US5973903A (en) * 1997-12-12 1999-10-26 Transdigm, Inc. Fuel line systems with electric charge buildup prevention
US6740236B2 (en) * 2001-09-25 2004-05-25 Kuss Corporation Fuel filter assembly having a conductive spring

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US500488A (en) * 1893-06-27 Simeon d
US1592175A (en) * 1924-07-10 1926-07-13 U G I Contracting Company Electric insulation for metal pipes
GB536846A (en) * 1940-01-11 1941-05-29 James Hoyle Mcguire Improvements in insulating pipe couplings
US2693223A (en) * 1952-02-21 1954-11-02 Goodrich Co B F Method of making flexible hollow connections
US2761979A (en) * 1953-04-03 1956-09-04 Barlow Corp Protection of pipe lines
US2985466A (en) * 1958-05-27 1961-05-23 Martin Co Rigid fuel line coupling with inspection means
US4406467A (en) * 1982-12-06 1983-09-27 Atlantic Richfield Company High pressure electrical isolation flange gasket
GB2133490B (en) * 1983-01-12 1986-02-26 Pd Oil And Chemical Storage Lt Pipe coupling
DE3641062A1 (en) * 1986-12-01 1988-06-16 Kyburz & Cie Insulating pipe connection
FR2617568B1 (en) * 1987-07-02 1989-10-20 Aerospatiale TUBE FOR THE CIRCULATION OF A FLAMMABLE FLUID, AND PIPING MADE FROM SUCH TUBES
US4971268A (en) * 1988-11-23 1990-11-20 The Boeing Company Dielectric support and wear sleeve
CN2711496Y (en) * 2004-06-17 2005-07-20 苏州市燃气设备阀门制造有限公司 Insulation joint for gas pipeline
JP4995823B2 (en) 2005-09-29 2012-08-08 エアバス オペレーションズ、ソシエダ リミタダ How to protect a fuel tank made of composite material from discharge

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2393003A (en) * 1944-05-03 1946-01-15 Smith Minton Larkin Kidney catheter
US4008937A (en) * 1974-09-20 1977-02-22 Stanley Aviation Corporation Coupling assembly
US4346428A (en) * 1980-06-05 1982-08-24 Stanley Aviation Corp. Coupling assembly with bonding jumper
US4891732A (en) * 1986-11-28 1990-01-02 British Aerospace Plc Anti-lightning strike fasteners for composite material aircraft structures
US5034157A (en) * 1990-03-16 1991-07-23 Itt Corporation Injection moldable composite
US5959828A (en) * 1996-07-16 1999-09-28 Hydraflow Coupling with insulated flanges
US5973903A (en) * 1997-12-12 1999-10-26 Transdigm, Inc. Fuel line systems with electric charge buildup prevention
US6740236B2 (en) * 2001-09-25 2004-05-25 Kuss Corporation Fuel filter assembly having a conductive spring

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20100003840A1 (en) * 2008-07-02 2010-01-07 Eaton Corporation Dielectric Isolators
US20100003438A1 (en) * 2008-07-02 2010-01-07 Miller Waste Mills d/b/a RTP Company Injection moldable, thermoplastic composite materials
US8003014B2 (en) 2008-07-02 2011-08-23 Eaton Corporation Dielectric isolators
US9136036B2 (en) 2008-07-02 2015-09-15 Miller Waster Mills Injection moldable, thermoplastic composite materials
US9234615B2 (en) 2008-07-02 2016-01-12 Eaton Corporation Dielectric isolators
US9618148B2 (en) 2008-07-02 2017-04-11 Eaton Corporation Dielectric isolators
US10040568B2 (en) 2013-01-30 2018-08-07 Short Brothers Plc Electrical protector

Also Published As

Publication number Publication date
EP1964777A1 (en) 2008-09-03
CA2634222A1 (en) 2007-07-05
WO2007074177A1 (en) 2007-07-05
CA2634222C (en) 2013-05-14
CN101346281A (en) 2009-01-14
ES2650553T8 (en) 2018-03-01
EP1964777A4 (en) 2014-07-02
CN101346281B (en) 2011-03-16
US20070145190A1 (en) 2007-06-28
EP1964777B1 (en) 2017-08-30
BRPI0520793A2 (en) 2009-05-26
ES2650553T3 (en) 2018-01-19

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